NASA/AMES A-03 AIRFOIL (ames03-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/AMES A-03 AIRFOIL (ames03-il) Reynolds number: 100,000 Max Cl/Cd: 34.42 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ames03-il-100000.txt Download as CSV file: xf-ames03-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/AMES A-03 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4430 0.09734 0.09326 -0.0125 1.0000 0.1228
-9.250 -0.4760 0.09194 0.08794 -0.0204 1.0000 0.1246
-9.000 -0.5688 0.09756 0.09338 -0.0028 1.0000 0.1152
-8.750 -0.5655 0.09325 0.08908 -0.0063 1.0000 0.1205
-8.500 -0.6031 0.08614 0.08190 -0.0228 1.0000 0.1244
-8.250 -0.5843 0.08136 0.07721 -0.0208 1.0000 0.1278
-8.000 -0.5712 0.07823 0.07409 -0.0207 1.0000 0.1339
-7.750 -0.6029 0.07290 0.06842 -0.0289 1.0000 0.1406
-7.500 -0.5730 0.07003 0.06578 -0.0253 1.0000 0.1478
-7.250 -0.6068 0.06736 0.06272 -0.0266 1.0000 0.1553
-7.000 -0.5838 0.06428 0.05993 -0.0233 1.0000 0.1626
-5.750 -0.5710 0.03821 0.03115 -0.0171 1.0000 0.0792
-5.500 -0.5544 0.03461 0.02716 -0.0156 1.0000 0.0749
-5.250 -0.5351 0.03159 0.02358 -0.0141 1.0000 0.0728
-5.000 -0.5147 0.02975 0.02143 -0.0130 1.0000 0.0752
-4.750 -0.4921 0.02778 0.01908 -0.0120 1.0000 0.0763
-4.500 -0.4681 0.02599 0.01695 -0.0110 1.0000 0.0774
-4.250 -0.4435 0.02463 0.01528 -0.0101 1.0000 0.0803
-4.000 -0.4188 0.02314 0.01374 -0.0097 1.0000 0.0860
-3.750 -0.3936 0.02208 0.01260 -0.0091 1.0000 0.0919
-3.500 -0.3685 0.02095 0.01149 -0.0086 1.0000 0.1004
-3.250 -0.3440 0.02003 0.01064 -0.0082 1.0000 0.1136
-3.000 -0.3195 0.01912 0.00988 -0.0078 1.0000 0.1354
-2.750 -0.2931 0.01762 0.00897 -0.0080 1.0000 0.2143
-2.500 -0.2865 0.01531 0.00954 -0.0014 1.0000 0.8086
-2.250 -0.2778 0.01567 0.00993 0.0048 1.0000 0.9022
-2.000 -0.1668 0.01688 0.01071 -0.0083 1.0000 0.9925
-1.750 -0.1334 0.01687 0.01050 -0.0107 1.0000 1.0000
-1.500 -0.1314 0.01664 0.01017 -0.0073 1.0000 1.0000
-1.250 -0.1269 0.01647 0.00988 -0.0042 1.0000 1.0000
-1.000 -0.1182 0.01637 0.00966 -0.0018 1.0000 1.0000
-0.750 -0.0859 0.01655 0.00968 -0.0037 0.9959 1.0000
-0.500 -0.0227 0.01709 0.01005 -0.0113 0.9850 1.0000
-0.250 0.0374 0.01756 0.01040 -0.0181 0.9738 1.0000
0.000 0.1042 0.01801 0.01076 -0.0258 0.9599 1.0000
0.250 0.1889 0.01828 0.01098 -0.0363 0.9422 1.0000
0.500 0.2555 0.01839 0.01108 -0.0431 0.9267 1.0000
0.750 0.2874 0.01857 0.01126 -0.0437 0.9140 1.0000
1.000 0.3145 0.01872 0.01142 -0.0432 0.9008 1.0000
1.250 0.3382 0.01881 0.01153 -0.0418 0.8867 1.0000
1.500 0.3592 0.01881 0.01156 -0.0397 0.8718 1.0000
1.750 0.3783 0.01868 0.01145 -0.0368 0.8560 1.0000
2.000 0.3957 0.01838 0.01118 -0.0333 0.8397 1.0000
2.250 0.4112 0.01789 0.01071 -0.0291 0.8227 1.0000
2.500 0.4268 0.01729 0.01016 -0.0252 0.8003 1.0000
2.750 0.4406 0.01628 0.00916 -0.0198 0.7779 1.0000
3.000 0.4573 0.01517 0.00810 -0.0155 0.7369 1.0000
3.250 0.4722 0.01387 0.00660 -0.0100 0.6039 1.0000
3.500 0.4827 0.01442 0.00582 -0.0049 0.4478 1.0000
3.750 0.5060 0.01527 0.00620 -0.0042 0.4021 1.0000
4.000 0.5306 0.01596 0.00660 -0.0037 0.3776 1.0000
4.250 0.5562 0.01659 0.00708 -0.0033 0.3591 1.0000
4.500 0.5822 0.01723 0.00759 -0.0031 0.3435 1.0000
4.750 0.6084 0.01793 0.00815 -0.0029 0.3305 1.0000
5.000 0.6352 0.01858 0.00876 -0.0029 0.3181 1.0000
5.250 0.6622 0.01926 0.00948 -0.0029 0.3064 1.0000
5.500 0.6890 0.02003 0.01023 -0.0029 0.2959 1.0000
5.750 0.7155 0.02089 0.01096 -0.0028 0.2858 1.0000
6.000 0.7427 0.02158 0.01184 -0.0030 0.2750 1.0000
6.250 0.7695 0.02246 0.01277 -0.0030 0.2648 1.0000
6.500 0.7959 0.02341 0.01363 -0.0030 0.2550 1.0000
6.750 0.8226 0.02418 0.01462 -0.0032 0.2440 1.0000
7.000 0.8487 0.02515 0.01574 -0.0033 0.2333 1.0000
7.250 0.8746 0.02615 0.01674 -0.0033 0.2232 1.0000
7.500 0.9003 0.02696 0.01768 -0.0033 0.2118 1.0000
7.750 0.9253 0.02795 0.01889 -0.0033 0.2000 1.0000
8.000 0.9497 0.02885 0.01995 -0.0033 0.1881 1.0000
8.250 0.9740 0.02958 0.02076 -0.0031 0.1763 1.0000
8.500 0.9981 0.03004 0.02121 -0.0030 0.1641 1.0000
8.750 1.0217 0.03037 0.02153 -0.0028 0.1514 1.0000
9.000 1.0438 0.03078 0.02208 -0.0025 0.1380 1.0000
9.250 1.0648 0.03129 0.02267 -0.0021 0.1246 1.0000
9.500 1.0845 0.03207 0.02354 -0.0015 0.1115 1.0000
9.750 1.1029 0.03329 0.02493 -0.0008 0.0996 1.0000
10.000 1.1196 0.03497 0.02683 0.0000 0.0894 1.0000
10.250 1.1358 0.03700 0.02902 0.0008 0.0818 1.0000
10.500 1.1520 0.03888 0.03103 0.0017 0.0757 1.0000
10.750 1.1641 0.04176 0.03414 0.0027 0.0711 1.0000
11.000 1.1716 0.04435 0.03713 0.0040 0.0670 1.0000
11.250 1.1823 0.04661 0.03951 0.0050 0.0638 1.0000
11.500 1.1900 0.05070 0.04366 0.0059 0.0616 1.0000
11.750 1.1802 0.05439 0.04786 0.0078 0.0609 1.0000
12.000 1.1628 0.05820 0.05205 0.0098 0.0605 1.0000
12.250 1.1411 0.06252 0.05670 0.0111 0.0604 1.0000
12.500 1.1166 0.06757 0.06203 0.0112 0.0604 1.0000
12.750 1.0896 0.07349 0.06818 0.0099 0.0607 1.0000
13.000 1.0611 0.08048 0.07537 0.0071 0.0611 1.0000
13.250 1.0318 0.08877 0.08380 0.0027 0.0616 1.0000
13.500 0.8312 0.15255 0.14747 -0.0383 0.0971 1.0000
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